Passenger service unit pod assembly

ABSTRACT

A personal service unit pod assembly configured to be positioned in the interior of an aircraft. The personal service unit pod assembly includes a personal service unit pod and a panel positioned directly above and affixed to the personal service unit pod. The pod includes a housing with a lens assembly and a pod interior, a first reading light positioned within the pod interior and configured to shine light below the bottom of the housing, and cabin lighting positioned in the housing and configured to shine light through the lens assembly and above the housing. The panel includes connectors that are configured to secure the personal service unit pod assembly to a component within the aircraft.

CROSS REFERENCE TO RELATED APPLICATIONS

This application is a continuation-in-part of U.S. patent applicationSer. No. 13/765,646, filed Feb. 12, 2013, which claims the benefit ofU.S. Provisional Application No. 61/598,856, filed Feb. 14, 2012, andU.S. Provisional Application No. 61/598,816, filed Feb. 14, 2012, whichare all herein incorporated by reference in their entireties.

FIELD OF THE INVENTION

The present invention relates generally to aircraft passenger serviceunits, and more particularly to a personal service unit pod assembly.

BACKGROUND OF THE INVENTION

Commercial aircraft, such as the Airbus A320 or Boeing 737 are typicallyconstructed from modular components, the size, weight and constructionof which are dictated by many considerations, including fuselagedimensions, aesthetic and safety considerations. Many of theserequirements are imposed by law or regulation. Aircraft components, suchas overhead stowage compartments, seats, lavatories, galleys, lightingsystems, etc. are all required to function within strictly confinedspaces.

Manufacturers of aircraft are constantly refining interior aircraftdesigns to achieve more comfort and utility for passengers and crewwithin carrier-imposed restraints on cost, weight, maintenancedown-time, and safety. Commercial passenger aircraft generally includeoverhead luggage storage bins mounted from the ceiling, walls or otherstructural portion of the aircraft over the passenger seats. These binsare designed to accommodate the size, shape, and weight of passengercarry-on luggage.

Other overhead storage bin assemblies are well known in the art. Forexample, see U.S. Patent Publication No. 2011/0253837 published Oct. 20,2011, U.S. Pat. No. 4,637,642 issued on Jan. 20, 1987 and U.S. Pat. No.5,567,028 issued on Oct. 22, 1996, the entireties of which are herebyincorporated by reference.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is a side elevational view of two pivot bin assemblies inaccordance with a preferred embodiment of the present invention showinga first pivot bin assembly in an open position and a second pivot binassembly in a closed position;

FIG. 2 is a perspective view of a portion of an aircraft cabin with aseries of pivot bin assemblies installed therein;

FIG. 3 is a perspective view of the pivot bin assemblies of FIG. 1;

FIG. 4 is a perspective view of the pivot bin assemblies of FIG. 1 withluggage therein;

FIG. 5 is a perspective view of the pivot bin assemblies of FIG. 1 withone of the bucket exploded therefrom;

FIG. 6 is a cross-sectional view taken along line 6-6 of FIG. 1;

FIG. 7A is a cross-sectional view taken along the same line as FIG. 7A,but showing an alternative embodiment for securing the bucket to theupper housing;

FIG. 7B is a cross-sectional view of a portion of the pivot binassemblies of FIG. 1;

FIG. 7C is a cross-sectional view taken along line 7C-7C of FIG. 1;

FIG. 8 is a cross-sectional view of one of the pivot bin assemblies ofFIG. 1 and showing how a standard piece of luggage fits therein;

FIG. 9 is a cross-sectional view of one of the pivot bin assemblies ofFIG. 1 with the PSU channel omitted;

FIG. 10 is a cross-sectional view of the a pivot bin assembly with adifferent valence;

FIG. 11 is a detailed cross-sectional view showing a rotary damper pivotmechanism providing the pivot point between the side panel and thebucket;

FIG. 12 is a detailed cross-sectional view showing a pivot axle as thepivot mechanism providing the pivot point between the side panel and thebucket;

FIG. 13 is an elevational view showing the first latch assembly in thelatched position;

FIG. 14 is an elevational view showing the first latch assembly in theunlatched position;

FIG. 15 is a cross-sectional view of the first latch assembly in thelatched position;

FIG. 16 is perspective view of a portion of an aircraft cabin showing aplurality of pivot bin assemblies and PSU pods installed therein andshowing an empty PSU channel;

FIG. 17A is a perspective view of the interior of an aircraft showing aseries of PSU pod assemblies installed therein with cabin lightingshining upwardly;

FIG. 17B is a perspective view of the interior of an aircraft showing aseries of PSU pod assemblies installed therein with cabin lightingshining outwardly;

FIG. 17C is a perspective view of the interior of an aircraft showing aseries of PSU pod assemblies installed therein with cabin lightingshining downwardly;

FIG. 18 is a cross-sectional view of a PSU pod assembly and showing thepassenger components and system components;

FIG. 19A is a side schematic view of a portion of a prior art aircraftshowing a series of seats with the passenger components and systemcomponents located thereabove in the PSU channel;

FIG. 19B is an end schematic view of a portion of a prior art aircraftshowing a series of seats with the passenger components and systemcomponents located thereabove in the PSU channel;

FIG. 20A is a side schematic view of a portion of an aircraft showing aseries of seats with the passenger components and system componentslocated thereabove;

FIG. 20B is an end schematic view of a portion of an aircraft showing aseries of seats with the passenger components and system componentslocated thereabove;

FIG. 21 is a side elevational view of an overhead storage compartmentwith a PSU pod assembly in accordance with a preferred embodiment of thepresent invention;

FIG. 22 is a perspective view of the PSU pod assembly of FIG. 21;

FIG. 23 is an exploded perspective view of the PSU pod assembly of FIG.21;

FIG. 24 is a cross-sectional view of the PSU pod assembly of FIG. 21;and

FIG. 25 is a perspective view of the interior of an aircraft showing aseries of PSU pod assemblies installed therein.

Like numerals refer to like parts throughout the several views of thedrawings.

SUMMARY OF THE PREFERRED EMBODIMENTS

In accordance with a first aspect of the present invention there isprovided a personal service unit pod assembly configured to bepositioned in the interior of an aircraft. The personal service unit podassembly includes a personal service unit pod and a panel positioneddirectly above and affixed to the personal service unit pod. The podincludes a housing with a lens assembly and a pod interior, a firstreading light positioned within the pod interior and configured to shinelight below the bottom of the housing, and cabin lighting positioned inthe housing and configured to shine light through the lens assembly andabove the housing. The panel includes connectors that are configured tosecure the personal service unit pod assembly to a component within theaircraft. In a preferred embodiment, the personal service unit podassembly includes a light halo secured within the pod interior. Thecabin lighting is seated on the light halo. Preferably, the housingincludes a gasper recess, and at least one gasper is positioned in thegasper recess. Preferably, the housing includes a reading light openingdefined in the bottom thereof, and the first reading light is alignedwith and configured to shine light through the reading light opening.

In a preferred embodiment, a bezel is associated with the reading lightopening, and a switch that operates the first reading light ispositioned in the bezel. Preferably, the panel includes a centralopening defined therethrough. At least one wire extends from the firstreading light through the opening and above the panel. In a preferredembodiment, a downward facing channel extends at least partially aroundthe central opening, and the lens assembly includes a flange extendingupwardly therefrom that is received in and secured in the channel.Preferably, the cabin lighting is an LED strip that extends generallyaround the reading light.

In accordance with another aspect of the present invention there isprovided an aircraft that includes a cabin that has at least onepersonal service unit channel positioned therein that includes personalservice unit rails extending therealong, and a personal service unit podassembly connected to the rails. The personal service unit pod assemblyincludes a panel and a housing generally positioned below the panel. Thepanel includes connectors that are connected to the personal serviceunit rails such that the panel is positioned beneath the personalservice unit channel. The housing includes a lens assembly and defines ahousing interior, at least a first reading light positioned within thepod interior and configured to shine light below the bottom of thehousing, and cabin lighting positioned in the housing and configured toshine light through the lens assembly and above the housing.

In a preferred embodiment, the panel includes a central opening therein,the housing includes an upper or central opening therein, and at leastone wire extends from the first reading light through the upper openingand the central opening and into the personal service unit channel.Preferably, the housing includes at least one vent opening definedtherein that is in air flow communication with a duct positioned in thepersonal service unit channel.

In accordance with yet another aspect of the present invention there isprovided a personal service unit pod assembly configured to bepositioned in the interior of an aircraft that includes a panel having acentral opening defined therethrough, and a housing that includes alower housing portion and an upper housing portion that cooperate todefine a housing interior. The upper housing portion includes a centralopening defined therein and is configured to allow light to shinetherethrough. The assembly also includes at least a first reading lightpositioned within the housing interior and configured to shine lightbelow the bottom of the housing. At least one wire from the firstreading light extends through the central openings in the housing andthe panel. The assembly also includes cabin lighting positioned in thehousing and configured to direct light generally upwardly and throughthe upper housing portion.

In a preferred embodiment, the panel includes connectors on top thereofthat are configured to secure the personal service unit pod assembly toa component within the aircraft. Preferably, the personal service unitpod assembly includes a light halo secured within the pod interior andthe cabin lighting is seated on the light halo. The light halo and upperhousing portion cooperate to define a light tunnel within the housinginterior, and the cabin lighting is positioned in the light tunnel.

In accordance with another aspect of the present invention there isprovided a PSU pod assembly that is configured to be positioned in theinterior of an aircraft. The PSU pod assembly includes a PSU pod thatincludes a housing that includes a top, a bottom and first, second,third and fourth sides that cooperate to define a pod interior and apanel positioned above and connected to the PSU pod. The PSU podincludes at least first and second reading lights positioned within thepod interior that are configured to shine light below the housing andcabin lights positioned on or in the housing that are configured toshine light above the housing. The panel includes connectors that areconfigured to secure the PSU pod assembly to a component within theaircraft. In a preferred embodiment, the PSU pod assembly includes alens assembly positioned adjacent the cabin lights. Preferably, thehousing includes at least one vent opening defined therein. In apreferred embodiment, the housing includes at least first and secondreading light openings defined therein, and the first and second readinglights are aligned with and configured to shine light through the firstand second reading light openings, respectively and the housing isspaced from the panel and the cabin lighting is positioned between thepanel and the housing.

In accordance with another aspect of the present invention there isprovided an aircraft that includes a cabin that has at least one PSUchannel positioned therein that has a length and includes PSU railsextending therealong, a plurality of system components positioned alongthe length of the PSU channel, and a plurality of PSU pods that eachcomprise a housing surrounding a passenger component bundle. The PSUpods are positioned below the system components. In a preferredembodiment, the aircraft includes a plurality of panels that includeconnectors that are connected to the PSU rails. Each PSU pod ispositioned below a panel. Preferably, each passenger component bundleincludes at least two reading lights configured to shine light below thehousing and each PSU pod includes cabin lights positioned on or in thehousing that are configured to shine light above the housing.Preferably, the at least two reading lights are not positioned withinthe PSU channel. In a preferred embodiment, each of the housings of thePSU pods includes at least one vent opening defined therein that is inair flow communication with a duct positioned in the PSU channel.Preferably, the plurality of panels at least partially define andenclose the PSU channel and define a first height. The PSU pods arepositioned below the first height and the PSU channel is positionedabove the first height.

In accordance with yet another aspect of the present invention there isprovided a method performed in the cabin of an aircraft that includes aplurality of rows of passenger seats positioned therein. The methodincludes positioning a first PSU pod within the cabin of the aircraftabove at least a first passenger seat within a first row and below a PSUchannel that contains system components therein and positioning a secondPSU pod within the cabin of the aircraft above at least a secondpassenger seat within a second row and below the PSU channel. The firstPSU pod includes a housing that has cabin lighting associated therewithand the second PSU pod includes a housing that has cabin lightingassociated therewith. A first distance or pitch is defined between thefirst seat and the second seat and a second distance or pitch is definedbetween the first PSU pod and the second PSU pod. The first distance andthe second distance are approximately the same. It will be appreciatedby those skilled in the art that cabin lighting is not usually passengerrow specific, but is tailored to the length of the aircraft. In apreferred embodiment, the method includes the step of switching on thecabin lighting from a first location that is remote from the first andsecond passenger seats. In a preferred embodiment, the first and secondhousings each include reading lights associated therewith, and themethod includes the step of switching on at least one of the readinglights associated with the first housing from a second location adjacentthe first passenger seat. The cabin is separated into a passenger areaand a crew area, and the first location is in the crew area. Preferably,the first housing is positioned below and connected to a first panelthat at least partially encloses and defines the PSU channel, and thesecond housing is positioned below and connected to a second panel thatat least partially encloses and defines the PSU channel. In a preferredembodiment, the method further includes the step of positioning a thirdPSU pod within the cabin of the aircraft above at least a thirdpassenger seat within a third row and below the PSU channel. The thirdPSU pod includes a housing that has cabin lighting associated therewith.A third distance is defined between the second seat and the third seatand a fourth distance is defined between the second PSU pod and thethird PSU pod. The first distance, second distance, third distance andfourth distance are approximately the same.

In accordance with another aspect of the present invention there isprovided an overhead stowage bin assembly that is configured to receiveluggage and be positioned in the interior of an aircraft, the overheadstowage bin assembly includes an enclosure that includes a door, bucketor tray that is openable to receive luggage in an enclosure interior.The enclosure includes an integral PSU channel formed therewith andincludes first and second rails that, when the overhead stowage binassembly is positioned in an aircraft, extend generally parallel to alongitudinally extending axis of the aircraft. The overhead stowage binassembly includes at least one panel that is connected to the first andsecond rails and partially defines the PSU channel and a PSU podpositioned below and connected to the panel. The PSU pod includes ahousing that includes a top, a bottom and first, second, third andfourth sides that cooperate to define a pod interior, at least first andsecond reading lights positioned within the pod interior and configuredto shine light below the housing, and cabin lights positioned on or inthe housing and configured to shine light above the housing. In apreferred embodiment, the enclosure includes an ECS channel integraltherewith that is separate from the PSU channel.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

The following description and drawings are illustrative and are not tobe construed as limiting. Numerous specific details are described toprovide a thorough understanding of the disclosure. However, in certaininstances, well-known or conventional details are not described in orderto avoid obscuring the description. References to one or an embodimentin the present disclosure can be, but not necessarily are references tothe same embodiment; and, such references mean at least one of theembodiments.

Reference in this specification to “one embodiment” or “an embodiment”means that a particular feature, structure, or characteristic describedin connection with the embodiment is included in at least one embodimentof the-disclosure. The appearances of the phrase “in one embodiment” invarious places in the specification are not necessarily all referring tothe same embodiment, nor are separate or alternative embodimentsmutually exclusive of other embodiments. Moreover, various features aredescribed which may be exhibited by some embodiments and not by others.Similarly, various requirements are described which may be requirementsfor some embodiments but not other embodiments.

The terms used in this specification generally have their ordinarymeanings in the art, within the context of the disclosure, and in thespecific context where each term is used. Certain terms that are used todescribe the disclosure are discussed below, or elsewhere in thespecification, to provide additional guidance to the practitionerregarding the description of the disclosure. For convenience, certainterms may be highlighted, for example using italics and/or quotationmarks: The use of highlighting has no influence on the scope and meaningof a term; the scope and meaning of a term is the same, in the samecontext, whether or not it is highlighted.

It will be appreciated that the same thing can be said in more than oneway. Consequently, alternative language and synonyms may be used for anyone or more of the terms discussed herein. No special significance is tobe placed upon whether or not a term is elaborated or discussed herein.Synonyms for certain terms are provided. A recital of one or moresynonyms does not exclude the use of other synonyms. The use of examplesanywhere in this specification including examples of any terms discussedherein is illustrative only, and is not intended to further limit thescope and meaning of the disclosure or of any exemplified term.Likewise, the disclosure is not limited to various embodiments given inthis specification.

Without intent to further limit the scope of the disclosure, examples ofinstruments, apparatus, methods and their related results according tothe embodiments of the present disclosure are given below. Note thattitles or subtitles may be used in the examples for convenience of areader, which in no way should limit the scope of the disclosure. Unlessotherwise defined, all technical and scientific terms used herein havethe same meaning as commonly understood by one of ordinary skill in theart to which this disclosure pertains. In the case of conflict, thepresent document, including definitions, will control.

It will be appreciated that terms such as “front,” “back,” “top,”“bottom,” “side,” “short,” “long,” “up,” “down,” “aft,” “forward,”“inboard,” “outboard” and “below” used herein are merely for ease ofdescription and refer to the orientation of the components as shown inthe figures. It should be understood that any orientation of thecomponents described herein is within the scope of the presentinvention.

Referring now to the drawings, wherein the showings are for purposes ofillustrating the present invention and not for purposes of limiting thesame, FIGS. 1-16 show a pivot bin assembly 10. In particular, theinvention can be used on commercial passenger aircraft. However, this isnot a limitation on the present invention and the pivot bin assembly 10can be used elsewhere.

The present invention pivot bin assembly 10 employs a “clamshelldesign.” In a preferred embodiment, the pivot bin assembly 10 allows asmuch of the entire volume inside the bin as possible to be used,increasing volume and baggage capacity when compared to the prior art.The design and structure also provides a way to integrate systems suchas environmental control system (“ECS”) ducting and electrical.

As will be appreciated by those skilled in the art, within the cabin ofan aircraft, overhead stowage bins are typically secured to attachmentpoints, such as hard points and overhead and side attachments.Accordingly, a description of the attachment of the pivot bin assemblywill be omitted.

FIGS. 1-16 show a dual pivot bin assembly that is essentially two pivotbin assemblies 10 with a common strongback 12 and that can be installedtogether in the cabin of an aircraft. However, it will be understood bythose of ordinary skill in the art, that a single and separate pivot binassembly 10 with a single strongback 12 is within the scope of thepresent invention and is described and claimed herein. In anotherembodiment, more than two or multiple pivot bin assemblies 10 caninclude a common strongback 12. The figures show pivot bin assemblies 10that are positioned outboard on the aircraft. However, it will beappreciated, that the pivot bin assembly 10 can be used inboard on awide body aircraft. For example, two sets of back to back outboardfacing pivot bin assemblies 10 can include a common strongback 12.

In a preferred embodiment, the pivot bin assembly 10 includes thestrongback 12, a tray or bucket 14 with a first and a second pivotmechanism or pivot axle 16 a and 16 b on each side, and first and secondside panels 18 a and 18 b. With respect to each pivot bin assembly 10,the strongback 12 and first and second side panels 18 a and 18 b arereferred to herein together as the upper housing 26. Generally, thepivot bin assembly 10 includes the upper housing 26, which includes thestrongback 12 and the first and second side panels 18 a and 18 b, andthe bucket 14. The bucket 14 and upper housing 26 cooperate to define abin interior 36. In a preferred embodiment, the bucket 14 defines thelower portion of the bin interior 36 and the upper housing defines theupper portion of the bin interior 36.

In the embodiment shown in the figures, the strongback 12 and first andsecond side panels 18 a and 18 b are separate components. However, inanother embodiment, the strongback 12 and first and second side panels18 a and 18 b (the upper housing 26) can be a unitary component. In apreferred embodiment, the pivot bin assembly 10 includes a single piecebucket 14 that includes a bottom 28 and first and second opposing sides24 a and 24 b. In another embodiment, the bucket 14 can include multiplepieces, e.g., a three piece design that includes the bottom 28 and firstand second opposing sides 24 a and 24 b as separate components. It willbe appreciated by those of ordinary skill in the art that the bucket 14and upper housing 26 provide a “clamshell design,” where at least aportion of the bottom edge 19 a of the first side panel 18 a and thebottom edge 19 b of the second side panel 18 b and the front bottom edge12 a of the strongback 12 meet edge to edge with or abut the top edge 14a of the bucket 14. In a preferred embodiment, in the closed position,other than the rear top edge 28 b of the bottom 28 of the bucket 14 andthe area adjacent thereto and the strongback 12 (see FIG. 8), there islittle to no overlap between the bucket 14 and the upper housing 26. Ina preferred embodiment, other than the localized overlap between thefirst and second ears 20 a and 20 b and the first and second indentedportions 22 a and 22 b, in the closed position, there is no overlapbetween the first and second side panels 18 a and 18 b and the first andsecond sides 24 a and 24 b of the bucket 14. In other words, in apreferred embodiment, the bucket 14 does not enter the upper portion ofthe bin interior 36, which is defined by the upper housing 26, when thebucket 14 is pivoted to the closed position. It will be appreciated bythose skilled in the art, that not only does this increase stowagevolume and reduce weight by eliminating redundant paneling, but alsosignificantly decreases the number of parts needed for the entire pivotbin assembly 10, compared to the prior art. As shown in the figures, thestrongback 12 can include an integral valence 34 for lighting, ductingand/or other system components that can be generally hidden frompassenger view. In a preferred embodiment, the valence 34 is formed as aunitary portion of the strongback 12. However, this is not a limitationon the present invention and the valence 34 can be omitted. As will beappreciated by those skilled in the art, within the cabin of anaircraft, overhead stowage bins are typically secured to attachmentpoints, such as hard points and overhead and side attachments.Accordingly, a detailed description of the attachment of the pivot binassembly will be omitted.

When the bucket 14 is pivoted to the closed position, the first andsecond sides 24 a and 24 b of the bucket 14 are not received in theupper portion of the bin interior 36. In other words, in the portion ofthe first and second side panels 18 a and 18 b that do not include thefirst and second ears 20 a and 20 b and first and second indentedportions 22 a and 22 b, the first and second top edges 25 a and 25 b donot pass or overlap with the first and second bottom edges 19 a and 19 bwhen the bucket 14 is pivoted to the closed position. Preferably, thefirst and second top edges 25 a and 25 b and first and second bottomedges 19 a and 19 b abut one another. However, an embodiment is possiblewhere the first and second top edges 25 a and 25 b and first and secondbottom edges 19 a and 19 b are horizontally separated from one another,but, in a vertical direction, the first and second top edges 25 a and 25b do not pass or overlap with the first and second bottom edges 19 a and19 b when the bucket 14 is pivoted to the closed position.

In a preferred embodiment, the strongback 12, bucket 14 and first andsecond side panels 18 a and 18 b are made out of crush-core panel.However, this is not a limitation on the present invention and othermaterials can be used. In an exemplary embodiment, the single piecebucket 14 is made using crush core match metal molding. This creates acontinuous composite structure with a C-frame cross section that can bemade from a single mold. The continuous piece acts as a structuralI-beam. However, this structure is not a limitation on the presentinvention.

As shown in FIGS. 1-12, generally, first and second side panels 18 a and18 b include first and second pivot mechanisms 16 a and 16 b that areoperatively associated with the bucket 14, and allow the bucket 14 topivot with respect to the upper housing 26 between an open position anda closed position. Any type of pivot mechanism that allows the bucket 14to pivot with respect to the upper housing 26 is within the scope of thepresent invention. For example, the first and second pivot mechanisms 16a and 16 b can be pivot axles, as shown in FIG. 12. It will beappreciated that the first and second pivot mechanisms 16 a and 16 b oraxles pivot or rotate about a pivot axis. In a preferred embodiment, thefirst and second pivot mechanisms 16 a and 16 b are axially aligned suchthat the pivot axles rotate about the same axis A1, as shown in FIGS. 7Cand 8.

In a preferred embodiment, the first side panel 18 a includes a firstear 20 a and the second side panel 18 b includes a second ear 20 bextending downwardly therefrom. The first and second ears 20 a and 20 bmate with or are received in first and second indented portions 22 a and22 b that are formed in the first and second sides 24 a and 24 b of thebucket 14. As shown in the figures, preferably, the first and secondindented portions 22 a and 22 b extend inwardly into the interior of thebucket 14. However, in another embodiment, the indented portions canextend outwardly. Furthermore, in another embodiment, the ears canextend upwardly from the bucket and the indented portions can be definedinwardly or outwardly on the side panels of the upper housing.

In a preferred embodiment, the first side panel 18 a, first ear 20 a andthe first side 24 a of the bucket 14 (other than the first indentedportion 22 a) all are positioned in a generally common plane P1 (seeFIG. 6). Likewise, the second side panel 18 b, second ear 20 b and thesecond side 24 b of the bucket 14 (other than the second indentedportion 22 b) all are positioned in a generally common plane. In anotherembodiment, the first and second ears 20 a and 20 b can be part of thebucket 14 and the first and second indented portions 22 a and 22 b canbe defined in the first and second side panels 18 a and 18 b.

As discussed above, and as shown in FIGS. 6 and 8, in a preferredembodiment, in the closed position, the bottom edges of the first andsecond side panels 18 a and 18 b abut the top edges 25 a and 25 b of thefirst and second sides 24 a and 24 b of the bucket 14 (FIG. 6) and thefront bottom edge 12 a of the strongback 12 abuts the front top edge 28a of the bottom 28 of the bucket 14 (FIGS. 8 and 14). As is also shownin FIGS. 8 and 14, the bottom 28 of they bucket 14 includes a rear topedge 28 b that is positioned adjacent to but does not abut a rear bottomedge 12 b of the strongback 12. This allows a portion of the bottom 28of the bucket to overlap with the strongback 12 when the bucket 14pivots to the open position. It will be appreciated by those skilled inthe art that in a commercial embodiment, the bucket and/or upper housingmay include edge trim, seals or the like that cover the top edges of thebucket or the bottom edges of the upper housing. However, this is not alimitation on the present invention and any such components areconsidered part of the upper housing or bucket for purposes of theclaims appended hereto. In a preferred embodiment, the pivot binassembly 10 includes at least one stop member 15 (and preferably aplurality of step members) positioned within the bin interior 36 andthat maintains the bucket 14 in the open position and prevents it frompivoting too far. Any type of stop member 15 is within the scope of thepresent invention. For example, as shown in FIG. 3, the stop member 15can abut the angled top edge 14 b of the back of the bucket 14 and/orthe rear top edge 28 b of the bottom 28 of the bucket 28. The stopmember 15 can be a separate component or be built in to the upperhousing 26 (e.g., a ledge).

In a preferred embodiment, the first pivot mechanism 16 a extendsbetween the first ear 20 a and the first side 24 a of the bucket 14 andthe second pivot mechanism 16 b extends between the second ear 20 b andsecond first side 24 b of the bucket 14. As discussed above, the firstand second pivot mechanisms can be pivot axles on which the bucket 14can rotate. As shown in FIGS. 5-6 and 7B-7C, a portion of the firstpivot mechanism 16 a can be positioned in corresponding openings 32 aand 33 a in the first ear 20 a and first side 24 a, respectively, and aportion of the second pivot mechanism 16 b can be positioned incorresponding openings 32 b and 33 b in the second ear 20 b and secondside 24 b, respectively. In another embodiment, a pivot axle can extendfrom the bucket and into an opening in the ear or vice versa. Any pairof pivot mechanisms that are axially aligned and that allow the bucket14 to pivot with respect to the upper housing 26 is within the scope ofthe present invention.

As shown in FIG. 11, in a preferred embodiment, the first and secondpivot mechanism comprise first and second rotary dampers 17 a and 17 b.With respect to the first rotary damper 17 a, one of the housing 19 orthe axle 21 is secured within opening 32 a and the other is securedwithin opening 33 a. With respect to the second rotary damper 17 b, oneof the housing 19 or the axle 21 is secured within opening 32 b and theother is secured within opening 33 b. It will be appreciated that FIG.11 only shows the first rotary damper 17 a, but that second rotarydamper 17 b is a mirror image thereof. The first and second rotarydampers 17 a and 17 b can include covers 23 to secure them in place.

It will be understood that the first and second rotary dampers 17 a and17 b provide the ability to damp or control the descent or pivoting ofthe bucket when it pivots to the open position. In a preferredembodiment, the first and second rotary dampers can be the rotary dampertaught in U.S. patent application Ser. No. 61/598,836 and simultaneouslyfiled U.S. patent application Ser. No. 13/765,358 titled FreewheelingRotary Damping Mechanism naming inventors Steve Kearsey and RichardMcClure (attorney docket no. 71703-5038), the entireties of which areincorporated by reference. In another embodiment, the first and secondrotary dampers can be the rotary damper taught in U.S. patentapplication Ser. No. 61/598,846 and simultaneously filed U.S. patentapplication Ser. No. 13/765,435 titled Rotary Damping Mechanism WithPivotal Vanes naming inventors Steve Kearsey and Richard McClure(attorney docket no. 71703-5039), the entireties of which areincorporated by reference. In another embodiment, each of the first andsecond side panels 18 a and 18 b can include a cover 23 positioned onthe outside or the inside of the bin interior 36 and that secures thefirst and second side panels 18 a and 18 b to the bucket 14 and thatcovers and houses the first and second pivot mechanism 16 a and 16 b. Itwill be appreciated that any type of power assist (for raising orlowering the bucket) or damper is within the scope of the presentinvention. For example, the present invention can utilize a prior artdamper, such as a linear damper that includes a cylinder with a pistonand damping fluid therein or a spring for assist, as is known in theart.

As shown in FIGS. 1-5 and, more specifically in FIGS. 13-15, in apreferred embodiment, the pivot bin assembly 10 includes first andsecond latch assemblies 40 a and 40 b operatively associated with thefirst and second side panels 18 a and 18 b and the first and secondsides 24 a and 24 b of the bucket 14. Preferably, the first latchassembly 40 a includes a first hook portion 42 a 44 a and a firststriker portion and the second latch assembly 40 b includes a secondhook portion 42 b and a second striker portion 44 b. In a preferredembodiment, the first hook portion 42 a extends downwardly from thebottom edge 19 a of the first side panel 18 a and the first strikerportion 44 a is positioned in a first recess 41 a defined in the topedge 25 a of the first side 24 a of the bucket 14 and the second hookportion 42 b extends downwardly from the bottom edge 19 b of the secondside panel 18 b and the second striker portion 44 b is positioned in asecond recess 41 b defined in the top edge 25 b of the second side 24 bof the bucket 14. In another embodiment, the first hook portion 42 aextends upwardly from the top edge 25 a of the first side 24 a of thebucket 14 and the first striker portion 44 a is positioned in a firstrecess defined in the bottom edge of the first side panel 18 a, and thesecond hook portion 42 b extends upwardly from the top edge 25 b of thesecond side 24 b of the bucket 14 and the second striker portion 44 b ispositioned in a second recess defined in the bottom edge of the secondside panel 18 b. In another preferred embodiment, the first strikerportion 44 a extends downwardly from the bottom edge 19 a of the firstside panel 18 a and the first hook portion 42 a is positioned in a firstrecess 41 a defined in the top edge 25 a of the first side 24 a of thebucket 14 and the second striker portion 44 b extends downwardly fromthe bottom edge 19 b of the second side panel 18 b and the second hookportion 42 b is positioned in a second recess 41 b defined in the topedge 25 b of the second side 24 b of the bucket 14. In anotherembodiment, the first striker portion 44 a extends upwardly from the topedge 25 a of the first side 24 a of the bucket 14 and the first hookportion 42 a is positioned in a first recess defined in the bottom edgeof the first side panel 18 a, and the second striker portion 44 bextends upwardly from the top edge 25 b of the second side 24 b of thebucket 14 and the second hook portion 42 b is positioned in a secondrecess defined in the bottom edge of the second side panel 18 b. Thefirst and second latch assemblies 40 a and 40 b can be actuated manuallyor electronically. As shown in FIG. 5, the pivot bin assembly 10preferably includes an operating member 27 disposed on the bucket 14. Ina preferred embodiment, the operating member 27 comprises a switch thatis in electrical communication (with wires or wirelessly) with the firstand second latch assemblies 40 a and 40 b.

It will be appreciated that any type of latching mechanism that allowsthe bucket 14 to connect to the upper housing 26 is within the scope ofthe present invention. Furthermore, it will be appreciated that theterms first hook portion and second hook portion refer to the entireassembly secured to the upper housing in the figures. And, the termsfirst striker portion and second striker portion refer to the entireassembly secured to the upper housing in the figures. The hook portioncan be any latching mechanism that includes a hook or latch that mateswith or latches to a striker. FIGS. 13-15 show an exemplary embodimentof the first latch assembly 40 a. It will be understood that the secondlatch assembly 40 b includes essentially the same components. FIGS. 13and 15 show the first latch assembly 40 a in the latched position andFIG. 14 shows the first latch assembly 40 a in the unlatched position.Preferably, the first hook portion 42 a is mounted in a recess 29 a inthe first side panel 18 a and includes a housing 31 a, a hook 35 a andguide members 37 a that help guide the striker 39 a (which can besecured in place by a threaded fastener 51 a) into the desired position.As is known in the art, the hook 35 a can be mounted on a pivot pin andinclude a spring 43 a for urging it into the desired position.Preferably the first striker portion 44 a includes a housing 45 a thatdefines a guide recess 47 a defined therein and that is spanned by thestriker 39 a. In use, when the bucket 14 is pivoted to the closedposition, the guide members 37 a are received in the guide recess 47 a,and, as a result of the angle on the bottom edge of the hook 35 a andthe round shape of the striker 39 a, the hook 35 a is pivoted out of theway and the striker 39 a is received fully between the guide members 37a. As a result of the spring 43 a, the hook 35 a is urged into theposition shown in FIG. 13, and the first latch assembly 40 a is now inthe latched position.

It will be appreciated by those skilled in the art that by the first andsecond hook portions 42 a and 42 b extending downwardly from the firstand second side panels 18 a and 18 b and latching to first and secondstriker portions 44 a and 44 b, which are essentially embedded in thefirst and second sides 24 a and 24 b of the bucket 14 allows the topedge 14 a of the bucket 14 (i.e., top edges 25 a and 25 b and front topedge 28 a to abut the bottom edge (bottom edges 19 a and 19 b and frontbottom edge 12 a) of the upper housing 26. In other words, the firstside panel 18 a, the first side 24 a of the bucket 14 and the firstlatch assembly 40 a are all lined up generally vertically and the secondside panel 18 b, the second side 24 b of the bucket 14 and the secondlatch assembly 40 b are all lined up generally vertically.

The first and second latch assemblies 40 a and 40 b shown in the figuresare not a limitation on the present invention and any type of latchassembly or mechanism for securing the bucket 14 to the upper housing 26is within the scope of the present invention. For example, the pivot binassembly can include a center latch that connects the bucket to thestrongback.

As shown in FIGS. 4, 8 and 14, the inventive pivot bin assembly 10 isdesigned to stow standard Travel Pro 22″ bags or luggage 11 wheels firston their edge (this type of bag is referred to herein as “standardluggage”). As will be understood by those of ordinary skill in the art,storage of a maximum amount of luggage within overhead stowage bins isof utmost importance in passenger aircraft and the standard luggagediscussed herein is used as an industry standard when determining theamount of cargo that will fit into overhead stowage bins. As shown inFIG. 4, a piece of standard luggage 11 includes a top 11 a, a bottom 11b, a front 11 c, a back 11 d and two sides 11 e. Typically, the standardluggage 11 includes wheels on the bottom 11 b thereof. In a preferredembodiment of the present invention, a pivot bin assembly 10 can stow upto four pieces of standard luggage within the bin interior. However,this is not a limitation on the present invention. In anotherembodiment, the present invention can store more or less standardluggage.

In a preferred embodiment, the pivot axis A1 or pivot point provided bythe first and second pivot mechanisms 16 a and 16 b is not along thesame lengthwise axis as the luggage stored within the bin interior, butis instead non-centrally located. Furthermore, the center of gravity ofthe luggage in the bin interior is moved outboard when compared to theprior art and closer to the pivot axis A1, thereby making the bucket 14easier to close. Furthermore, compared to prior art pivot bins, thepivot bin assembly 10 can be moved further outboard from the aisle,thereby providing more passenger space and an open cabin feel. However,none of the statements that include comparisons to the prior art areintended to be a limitation on the present invention.

With reference to FIGS. 19A-19B, as will be appreciated by those ofordinary skill in the art, passenger aircraft typically include what isreferred to as a passenger service unit (“PSU”), which is situatedgenerally above each seat row (although not typically at the same pitchwith respect to each seat row) in the overhead panel above the passengerseats in the cabin of airliners. Amongst other things a PSU containsreading lights, loudspeakers, illuminated signs and automaticallydeployed oxygen masks and also gaspers providing conditioned air.Passenger service units typically include individual PSU panels 117 thatare specialized for each function (e.g., speaker panels, reading lightpanels, spacer panels, etc.) and that are positioned on rails 116 thatrun the length of the interior of the cabin. These individual functionalspecific panels are then configured to meet the aircraft and passengerneeds, typically resulting in the configuration and installation ofthree hundred or more specialized panels. These panels 117 are installedwithin and cover a PSU channel 118 that is filled with both passengerelements 112 (e.g., reading lights, gaspers, flight attendant buttons,etc.) and systems elements 114 (wiring, oxygen tanks/components, cabinlights and associated electronics, ducting, etc.) creating a ceiling 120above the passenger that restricts\bounds the passenger's head room. Asshown in FIG. 19A, there is a fixed distance or height H1 from the floor122 to the “ceiling” 120.

With reference to at least FIGS. 16-20B, in a preferred embodiment, thepivot bin assembly 10 includes an integrated PSU channel 50 and a PSUpod 52 for each passenger row. As discussed above, aircraft PSUstypically include two types of elements: passenger elements 112 (readinglights, gaspers/air vents and flight attendant call buttons) and systemselements 114 (wiring, oxygen tanks 113/components, cabin lights andassociated electronics, ducting, etc.). As shown in FIG. 18, the PSU pod52 provides a way to at least partially separate the passenger elementbundle 112 for each row from the systems elements bundle 114 for eachrow. By separating the passenger elements 112 from the systems elements114 that are typically installed in a PSU, a PSU pod 52 (for thepassenger elements 112) is configured or positioned independent of thesystems elements 114, which are positioned in the PSU channel 50. Asshown in FIGS. 18 and 20A, in a preferred embodiment, the passengerelements bundle 112 is positioned below the systems elements bundle 114.It will be appreciated that in another embodiment of the invention, thePSU pod 52 and PSU pod assembly 58 can be used with overhead binsdifferent than the clamshell design described herein. For example, thePSU pod assembly 58 can be used with other types of pivot bins or anoverhead stowage bin that is fixed but includes a pivotal door. The PSUpod assembly can be used with any overhead stowage bin that includes anenclosure for luggage and a PSU channel formed integrally therewith.

In a preferred embodiment, the PSU pod 52 preferably includes a housing54 that includes first, second, third and fourth sides 53 a, 53 b, 53 cand 53 d, a top 53 e and a bottom 53 f that cooperate to define a podinterior 58, a plurality of reading lights 60 (that are aligned with aneither extend through or shine light through reading light openings 54a), cabin lighting 62, a lens assembly 64 and a vent or gasper 66defined in the housing for gasping conditioned air. It will beappreciated that the housing can be circular, ovular or elliptical inshape. For purposes of this disclosure, these shapes are considered tohave first, second, third and fourth sides. In a preferred embodiment,the PSU pod 52 is part of a PSU pod assembly 58 that includes a panel 56that has connectors 70 a (such as hooks), that mate with rails orconnectors 70 b that are a part of the strongback 12 and extend in adirection that is generally parallel to the axis of the aircraft. In thefigures, “70” is used to designate the connection between 70 a and 70 b.It will be appreciated that any type of connection, such as hooks,rivets, threaded fasteners, magnets, snap fit arrangements or any othermethod of securing the panels 56 and PSU pod 52 to the upper housing 26or strongback 12 is within the scope of the present invention. The PSUpod 52 is connected to and extends or hangs downwardly from the panel56, thereby creating the PSU pod assembly 58. In another embodiment, thepanel can be omitted and the PSU pod itself can be connected to therails 70 b. When installed in an aircraft, wires for electricalconnection (to both the reading lights 60 and the cabin lighting 62) andducting for the gasper(s) 66 extends from the PSU channel 50 through anopening 56 a (or openings) in the panel 56 and down into the housing 54.The PSU pod 52 can include a flight attendant call button 72 thereon.

As discussed above, in a preferred embodiment, the PSU pod assembly 58also includes cabin lighting 62 that is associated with the PSU pod 52.The cabin lighting 62 can be any type of lighting (e.g., LEDs,incandescent, halogen, etc.) and can be positioned within or on housing54. In a preferred embodiment, the PSU pod assembly 58 also includes alens assembly 64 that helps direct light that shines from the cabinlighting 62 as desired. As is best shown in FIG. 17A, the light 62 afrom the cabin lighting 62 shines from the top of the PSU pod 52 andwashes along and down the panels 56, bucket 14 and sidewalls, etc. ofthe aircraft. As a result of this arrangement, in a preferredembodiment, the PSU pods 52 provide passenger specific reading lights 60that shine generally downwardly and outwardly and row specific cabinlighting that shines generally upwardly and outwardly. FIG. 17B showsanother embodiment, where the reading lights, vent and flight attendantcall button are omitted and the PSU pod 52 includes cabin lightingshining out the first, second, third and fourth sides 53 a-53 d. FIG.17C shows another embodiment, where the reading lights, vent and flightattendant call button are omitted and the PSU pod 52 includes cabinlighting shining out the bottom of the housing 54. These embodiments canalso include the reading lights, vent and flight attendant call button.These embodiments all create cabin lighting specifically for each row bypositioning the cabin lighting on or in the PSU pods 52.

With reference to FIGS. 20A-20B, as discussed above, generally, in thepresent invention, a passenger element bundle 112 is included in eachPSU pod 52 and the systems elements 114 are disposed within the PSUchannel 50 or at some other position above the ceiling defined by eitherthe overhead bins or the panels 56 used to hide the systems elements114. It will be understood that the systems elements 114 include bothrow specific elements (e.g., oxygen tanks/masks) and non-row specificelements (air ducts, electrical wiring, etc.). These elements are shownschematically in FIGS. 19A-20B as a box or bundle. However, it will beappreciated by those skilled in the art, that systems elements 114 canbe located at any position along the PSU channel 50. In a preferredembodiment, the systems elements 114 are stacked generally above the PSUpod 52 and the passenger elements 112. In other words, the PSU pod 52 ispositioned below the PSU channel 50 that houses the systems elements114. However, as discussed above, not all systems elements 114 will bepositioned directly above the passenger elements 112 or PSU pod 52. Inother words, the passenger elements 112 or PSU pod 52 or located at afirst level and the systems elements 114 are located at a second levelor height that is higher than the passenger elements 112 or PSU pod 52.

The PSU pod 52 changes the configuration and installation methodology ofthe prior art by using a row specific design and a completed channel 50built in to and defined within the pivot bin assembly 10. Compared tothe prior art, this helps eliminate or reduce unnecessary spacer panels.In a preferred embodiment, each PSU pod 52 has the same pitch oralignment with respect to each row of seats 124. It will be appreciatedthat the positioning of the PSU pod assembly 58 can be adjusted as aresult of the connection 70 between the connectors 70 a and the rails 70b. In other words, the PSU pod assembly 58 can slide fore or aft on therails 70 b. Furthermore, by reducing the number of components in the PSUchannel, the height of the panels can be raised (compared to the priorart), to a height H2, that is greater than the height H1 in a similarprior art aircraft. Furthermore, although the PSU pod 52 extenddownwardly below the panels 56, in a preferred embodiment, it can bepositioned at a height H1 that is the same or similar to the height ofthe prior art ceiling 120/panel 117 height. This allows the PSU pod 52to be positioned such that the height H2 provides more passenger spaceor headroom than the prior art and positions the PSU pod 52 and theelements therein or thereon (e.g., reading lights, vents, cabinlighting, etc.) at a consistent position or pitch for each row ofpassengers. In other words, passenger headroom height between PSU pods52 is increased when compared to the prior art. However, the positioningof the PSU pod 52 is not a limitation on the present invention. Inanother embodiment, they can be positioned lower than the prior artheight H1 and/or they can be positioned such that they have a differentpitch than each row.

In another embodiment, the cabin lighting can be omitted or more or lessreading lights can be included. The switches or buttons for the readinglights 60 can be positioned on the PSU pod 52 or elsewhere within reachof the passenger for which each reading light 60 is intended. In apreferred embodiment, the reading lights 60 are controlled by thepassengers seated in the row for which the PSU pod 52 is designated andthe cabin lighting 62 is controlled by the crew from a location remotefrom the passengers.

FIGS. 21-25 show another preferred embodiment of a PSU pod 76 and PSUpod assembly 77 that includes a gasper recess 78 having at least oneadjustable gasper 66 positioned therein. Each gasper 66 includes a ventopening through which air is controllably emitted. In other words, thegaspers 66 are inset with respect to the housing bottom 53 f.Preferably, the bottom of the housing 53 f is positioned below thebottom most point of the gaspers 66. In another embodiment, the gaspers66 may extend at least partially below the bottom of the housing 53 f.It will be appreciated that the number of gaspers 66 typicallycorresponds to the number of seats in a row. The gaspers 66 arepositioned in gasper openings 87 in the housing 54 and receive air froma duct 88.

As shown in FIG. 23-24, The PSU pod 76 includes a plurality of readinglights 60 that are aligned with and shine light through a single readinglight opening 54 a that has a transparent or translucent cover 79thereon and a bezel 80 therearound. In a preferred embodiment, thebuttons 82 for each of the reading lights 60 are positioned in the bezel80. This helps hide the buttons 82 and provides an aesthetic look. Inanother embodiment, the buttons can be positioned elsewhere. In anotherembodiment, the buttons can be capacitive touch buttons that are part ofthe housing. The PSU pod 76 can also include indicators 84 such asfasten seat belt, no smoking and wifi, etc. that are associated with thebottom 53 f of the housing 54 and are lighted by lights 86 therebehind.Buttons 82 for other purposes, such as flight attendant call, can alsobe positioned in the bezel 80 or elsewhere on the housing 54.

As shown in FIG. 23, in a preferred embodiment, the PSU pod assembly 77also includes a light halo 89 that supports and seats the cabin lights62, which, in this embodiment, is a strip 90 with a plurality of LEDs 91thereon. The light halo 89 includes a plurality of brackets 92 that matewith brackets 93 on the panel 56 and brackets/openings in the housing 54that are all secured together with fasteners, adhesive or otherattachment method. As shown in FIG. 23, the lens assembly 64 (which ispart of housing 54) preferably includes a generally vertically orientedsection 64 a and a generally horizontally oriented section 64 b. Thisallows the cabin lighting 62 to shine outwardly and upwardly. In otherwords, the housing 54 includes a lower housing portion 100 and an upperhousing portion, which is also referred to herein as the lens assembly64. The upper housing portion 64 includes a central opening 101. Asshown in FIG. 23, the light halo 89 and the lens assembly 84 cooperateto define a light tunnel 97 within the pod/housing interior 59 and inwhich the cabin lighting 62 is positioned.

As shown in FIGS. 23-24, the panel 56 includes a downward facing channel98 defined therein that extends at least partially around the centralopening 56 a. The lens assembly 64 includes a flange 99 extendingupwardly therefrom that is received in and secured in the channel 98.Threaded fasteners, rivets, adhesive or the like secure the flange 99within the channel 98. For example, fasteners can extend throughopenings 94 a and 94 b to secure the lens assembly 64 (and therefore thehousing 54) to the panel 56. The PSU pod assembly 77 can also include apanel stiffener 96.

When installed in an aircraft, wires 95 for electrical connection (toboth the reading lights 60, the cabin lighting 62, buttons 82 indicatorlights 86 and any other electrical components) and ducting 88 for thegasper(s) 66 extends from the PSU channel 50 through an opening 56 a (oropenings) in the panel 56 and down into the housing 54. The PSU pod 52can include a flight attendant call button 72 thereon.

With reference to FIG. 8, in a preferred embodiment, the pivot binassembly 10 includes an environmental control system (“ECS”) thatincludes ducting and electrical. In a preferred embodiment, thestrongback 12 serves as the enclosure of the ECS ducting. As discussedabove, at least a portion of the ECS components are positioned in thePSU channel 50. However, the pivot bin assembly 10 can also include atleast one further separate ECS channel 74. Electrical wire harnesses canbe directly attached to the pivot bin assembly 10 instead of theaircraft for an easier and cleaner installation, when compared to theprior art. However, the ECS channel can be omitted and the ducting,electrical, etc. can be connected to the aircraft in another embodiment.

Unless the context clearly requires otherwise, throughout thedescription and the claims, the words “comprise,” “comprising,” and thelike are to be construed in an inclusive sense, as opposed to anexclusive or exhaustive sense; that is to say, in the sense of“including, but not limited to.” As used herein, the terms “connected,”“coupled,” or any variant thereof, means any connection or coupling,either direct or indirect, between two or more elements; the coupling ofconnection between the elements can be physical, logical, or acombination thereof. Additionally, the words “herein,” “above,” “below,”and words of similar import, when used in this application, shall referto this application as a whole and not to any particular portions ofthis application. Where the context permits, words in the above DetailedDescription of the Preferred Embodiments using the singular or pluralnumber may also include the plural or singular number respectively. Theword “or” in reference to a list of two or more items, covers all of thefollowing interpretations of the word: any of the items in the list, allof the items in the list, and any combination of the items in the list.

The above-detailed description of embodiments of the disclosure is notintended to be exhaustive or to limit the teachings to the precise formdisclosed above. While specific embodiments of and examples for thedisclosure are described above for illustrative purposes, variousequivalent modifications are possible within the scope of thedisclosure, as those skilled in the relevant art will recognize Further,any specific numbers noted herein are only examples: alternativeimplementations may employ differing values, measurements or ranges.

The teachings of the disclosure provided herein can be applied to othersystems, not necessarily the system described above. The elements andacts of the various embodiments described above can be combined toprovide further embodiments. Any measurements or dimensions described orused herein are merely exemplary and not a limitation on the presentinvention. Other measurements or dimensions are within the scope of theinvention.

Any patents and applications and other references noted above, includingany that may be listed in accompanying filing papers, are incorporatedherein by reference in their entirety. Aspects of the disclosure can bemodified, if necessary, to employ the systems, functions, and conceptsof the various references described above to provide yet furtherembodiments of the disclosure.

These and other changes can be made to the disclosure in light of theabove Detailed Description of the Preferred Embodiments. While the abovedescription describes certain embodiments of the disclosure, anddescribes the best mode contemplated, no matter how detailed the aboveappears in text, the teachings can be practiced in many ways. Details ofthe system may vary considerably in its implementation details, whilestill being encompassed by the subject matter disclosed herein. As notedabove, particular terminology used when describing certain features oraspects of the disclosure should not be taken to imply that theterminology is being redefined herein to be restricted to any specificcharacteristics, features or aspects of the disclosure with which thatterminology is associated. In general, the terms used in the followingclaims should not be construed to limit the disclosures to the specificembodiments disclosed in the specification unless the above DetailedDescription of the Preferred Embodiments section explicitly defines suchterms. Accordingly, the actual scope of the disclosure encompasses notonly the disclosed embodiments, but also all equivalent ways ofpracticing or implementing the disclosure under the claims.

While certain aspects of the disclosure are presented below in certainclaim forms, the inventors contemplate the various aspects of thedisclosure in any number of claim forms. For example, while only oneaspect of the disclosure is recited as a means-plus-function claim under35 U.S.C. §112, ¶6, other aspects may likewise be embodied as ameans-plus-function claim, or in other forms, such as being embodied ina computer-readable medium. (Any claims intended to be treated under 35U.S.C. §112, ¶6 will include the words “means for”). Accordingly, theapplicant reserves the right to add additional claims after filing theapplication to pursue such additional claim forms for other aspects ofthe disclosure.

Accordingly, although exemplary embodiments of the invention have beenshown and described, it is to be understood that all the terms usedherein are descriptive rather than limiting, and that many changes,modifications, and substitutions may be made by one having ordinaryskill in the art without departing from the spirit and scope of theinvention.

What is claimed is:
 1. A personal service unit pod assembly configuredto be positioned in the interior of an aircraft, the personal serviceunit pod assembly comprising: a personal service unit pod that includesa housing that includes a lens assembly and defines a pod interior, atleast a first reading light positioned within the pod interior andconfigured to shine light below the bottom of the housing, and cabinlighting positioned in the housing and configured to shine light throughthe lens assembly and above the housing, a panel positioned directlyabove and affixed to the personal service unit pod, wherein the panelincludes connectors that are configured to secure the personal serviceunit pod assembly to a component within the aircraft.
 2. The personalservice unit pod assembly of claim 1 further comprising a light halosecured within the pod interior, wherein the cabin lighting is seated onthe light halo.
 3. The personal service unit pod assembly of claim 1wherein the housing includes a gasper recess, and wherein at least onegasper is positioned in the gasper recess.
 4. The personal service unitpod assembly of claim 1 wherein the housing includes a reading lightopening defined in the bottom thereof, and wherein the first readinglight is aligned with and configured to shine light through the readinglight opening.
 5. The personal service unit pod assembly of claim 4wherein a bezel is associated with the reading light opening, andwherein a switch that operates the first reading light is positioned inthe bezel.
 6. The personal service unit pod assembly of claim 1 whereinthe panel includes a central opening defined therethrough, wherein atleast one wire extends from the first reading light through the openingand above the panel.
 7. The personal service unit pod assembly of claim6 wherein a downward facing channel extends at least partially aroundthe central opening, and wherein the lens assembly includes a flangeextending upwardly therefrom that is received in and secured in thechannel.
 8. The personal service unit pod assembly of claim 2 whereinthe cabin lighting is an LED strip that extends generally around thereading light.
 9. An aircraft comprising: a cabin that has at least onepersonal service unit channel positioned therein, wherein the personalservice unit channel includes personal service unit rails extendingtherealong, and a personal service unit pod assembly that includes apanel and a housing generally positioned below the panel, wherein thepanel includes connectors that are connected to the personal serviceunit rails such that the panel is positioned beneath the personalservice unit channel, wherein the housing includes a lens assembly anddefines a housing interior, at least a first reading light positionedwithin the pod interior and configured to shine light below the bottomof the housing, and cabin lighting positioned in the housing andconfigured to shine light through the lens assembly and above thehousing.
 10. The aircraft of claim 9 wherein the panel includes acentral opening therein and wherein the housing includes an upperopening therein, and wherein at least one wire extends from the firstreading light through the upper opening and the central opening and intothe personal service unit channel.
 11. The aircraft of claim 9 whereinthe housing includes at least one vent opening defined therein, whereinthe vent opening is in air flow communication with a duct positioned inthe personal service unit channel.
 12. The personal service unit podassembly of claim 11 wherein the housing includes a gasper recess, andwherein at least one gasper is positioned in the gasper recess.
 13. Theaircraft of claim 9 wherein the housing further comprising a light halosecured within the housing interior, wherein the cabin lighting isseated on the light halo.
 14. A personal service unit pod assemblyconfigured to be positioned in the interior of an aircraft, the personalservice unit pod assembly comprising: a panel that includes a centralopening defined therethrough, a housing that includes a lower housingportion and an upper housing portion that cooperate to define a housinginterior, wherein the upper housing portion includes a central openingdefined therein and is configured to allow light to shine therethrough,at least a first reading light positioned within the housing interiorand configured to shine light below the bottom of the housing, whereinat least one wire from the first reading light extends through thecentral openings in the housing and the panel, and cabin lightingpositioned in the housing and configured to direct light generallyupwardly and through the upper housing portion.
 15. The personal serviceunit pod assembly of claim 14 wherein the panel includes connectors ontop thereof that are configured to secure the personal service unit podassembly to a component within the aircraft.
 16. The personal serviceunit pod assembly of claim 14 further comprising a light halo securedwithin the pod interior, wherein the cabin lighting is seated on thelight halo.
 17. The personal service unit pod assembly of claim 16wherein the light halo and upper housing portion cooperate to define alight tunnel within the housing interior, wherein the cabin lighting ispositioned in the light tunnel.
 18. The personal service unit podassembly of claim 14 wherein the housing includes a gasper recess, andwherein at least one gasper is positioned in the gasper recess.